Aeroplane.



F. G. LAMBERT.

AEROPLANE.

APPLICATIONTILEDOGT. 16, v1911.

Patented Apr. 30, 1912.

3 SHEETS-SHEET 1.

/V' ZKM.

I. C. LAMBERT.

ABROPLANE. APPLIOAT'ION 'FILED 001,216, 1911.

Patented Apr. 30, 1912.

3 SHEETS-SHEET 2.

' WITNESS/5S By ,ff-1f ATTORNEYS F. VG. LAMBERT.

AEROPLANE. n 'T114- 1 f y APPLICATION FILED 017116.11911.

1.-1f-, o2 ,4.,94`11.n

, Patented Apr. 30, 1912.

a SHBETPBHEBT a.

/NVENTH ATTORNEYS UNITED sTATEs PATENT oEEIoE.

FREDERICK C. LAMBERT, F NEW YORK, N. Y.

AEROPLANE.

' To all fwhom t may concern.'

' swing up andl down on the framework A;

Be it known that I, FREDERICK C. LAM- BERT, a citizen of the United States, and a resident of the city of New York, borough of the Bronx, in the county andState of New York, have invented a new and Ilmproved Aeroplane, of which the'following-g 1s a full, clear, and eXact description.

4The object of the invention is to provide a new and improved -aeroplane, arranged to provide a large sustaining surface for carry, ing a heavy load, to enable the avlator to readily maintain the equilibrium and thusl avoid undue swaying, and to permit easyf control of the sidewise steering means and the raising and lowering means. For thef purpose mentioned, use ismade of a-frame# j work carrying front and rear s'ustainlng;

planes slightly inclined upwardly and forwardly, a basket on the framework, under-l neath the said plane, for containing the. motor, aviator and passengers as well asthe j actu-ating mechanism, a propeller on the front end of the framework, a raising and lowering tail plane at-the rear end of the i framework, sidewise steering rudders, ailerons mounted to swing up and down intermediate the fixed sustaining planes, and; actuating means under the control' of the aviator for controlling the said tail plane,

l shafts K2 and'K3 A practical embodiment of theinvention is` represented in the accompanying draw,V ings forming a part of this specification,I in i which similar c aracters of reference indi- 'l tail plane J and the rudders K, K', use `is made of an actuating mechanism L ar,

steering rudders and ailerons;

cate correspondin parts in all the views.

Figure 1 is a p an view of the aeroplane; Fig. 2 is a side elevation of the same; Fig. 3 is a front end elevation of the same; Fig. 4 is a perspective view of the tail plane, steering rudders, ailerons and the a-ctuating mechanism for actuating the said parts; and Fig. 5 is a cross section of the actuating mea/11S.

taining plane C to approximately half wayv the distance between the sustaining planes C and D. Ailerons F'and F are mounted to extendingl reari Specification of Letters Patent. Patented Apr, 3()7 `1912 Application led October 16, 1911.

-Serial No. 654,832.

immediately in the rear of the side sustainlng planes E and E to maintain the aeroplane in the desired equilibrium by swinging the ailerons F and F simultaneously up and down but in opposite directions one as herelnafter more as well as for supporting a motor H for driving a propellerl arranged immediately in front of the forward pivoted at J a tail plane J adapted to swing up and down forA elevating or lowering the aeroplane when in flight, it being understood that when the tail plane is yswung downward from a horizontal position, the

aeroplane is directed downwardly, and when the tail plane J is swung upward from a horizontal position the aeroplane is directed upwardly.

v0n the framework A are mountedy vertically-disposed rudders K and K located equi-- distantly from the longitudinal center of the aeroplane, and the said rudders K andv K) are provided with vertically-disposed journaled in suitable bearings attached to the framework A immediately in the rear of the rear sustaining plane D.

In order tolcontrol the ailerons F, F the ranged in the cock pit G in front of the aviators seat G2, andthe said actuating mechanism L is arranged as follows, special reference being had to Figs. 4 and 5: A hollow post-N is provided at its lower end with transversely extending trunnions N.

j ournaled in suitable bearings N2v attached to A suitably'constructed framework A supy the bottom of the cock pit G. A link .N3 extending longitudinally is pivotally connected at its forward end to at its rear end the said link connected with an arm J2 depending from the pivotal end of the tail plane J so that when the post N is swung forward or. backward, a downward or upward-swinging motion is given to the tail plane J.

Within the hollow post N is mounted to turns a hollow spindle O provided on `its up- N3 is pivotally sustaining yplane C. On the rear end of the framework A is the post N, and` per end with a hand wheel O under the 'conextending horizontal arm F3 pivotally connected with one end of a lever F4 fulcrumed at its middle on a bracket F5 held in the L basket G, and the other end ofthe lever F4 is pivotally connected with an arm F6 secured to the shaft F7 of the aileron F. When the aviator turns the hand wheel O then the mechanism described imparts a simultaneous turning motion to the shafts F2 and F7 to swing the ailerons F and F simultaneously downwardor upward but in opposite directions one relative to the other. Thus when the wheel O is in. one direction the aileron F swings upward while the aileron F swings` downward. When the wind tends to swing, say, the right-hand side of the aeroplane downward and the left-hand side upward, then the aviator turns the hand wheel O so that aileron F swings downward while the aileron F swings upward, to cause the aeroplane to maintain its equilibrium in a sidewise direction and in a like manner when the wind tends to move the aeroplane downward at the left-hand side and upward at thevrighthand side, then the hand wheel O is turned in a reverse direction to swing the aileron F downward and v the aileron F upward.

y Wvithin the spindle O is mounted to turn a shaft P carrying at its upper end a hand wheel P located slightly above the hand wheel O so as to be within convenient reach of the aviator. On the lower end of the shaft P is secured a sidewise-extending arm P? connected by' a rearwardly-extending link P3 with a bell crank lever P4 fulcrumed on the framework A, and pivotally connected by transverse links P5, P6 with arms Kt, K5 secured on the lower ends of the shafts K2 and K3 of the rudders K and K. When the operator turns the hand wheel P then a sidewise swinging movement is given simultaneously to the rudders K, K in the same direction to steer the aeroplane to the right or to the left according to the direction in which the hand wheel P is turned.

From the foregoing it will be seen that the actuating mechanism L is within convenient reach of the aviator seated on the seat G2, it being understood that on rocking the post N forward or backward the tail plane J is swung up or down for lowering or raising purposes, and on turning the hand wheel O the ailerons F and F are swung simultaneously up or down in opposite directions for maintaining an equilibrium, and on 'turning the hand wheel l the rudders lli, K

5 simultaneously turned to the right or left marinai to steer the aeroplane in the desired direction.

' By constructing the aeroplane with front and rear sustaining planes@ and Dand the side sustaining planes E and E', a large sustaining surface-is provided to permit of carrying a heavy load, and by constructing the basket G in `the manner described comparativelyl little resistance is offered by the basket to the air, at the same time the aviator. and passengers are protected and the basket increasesthe sustaining area of the aeroplane. By Islightly inclining the sustaining planes C and D in a forward and upward direction the aeroplane is not liable to take a header, and surging of the aeroplane is reduced to 'a minimum.

Having thus described my invention, I claim as new and desire to secure by Letters Patent:

l. An aeroplane,comprising a framework, main sustaining planes fixed on the said framework one in front of the other and each slightly inclined upwardly and forwardly, side-sustaining planes fixed on the said framework and extending rearwardly from the front main sustaining, plane and terminating at their rear ends between the forward and rear main planes, and movable ailerons at the rear end of the said side sus' taining planes.

2. An aeroplane, comprising a framework, main sustaining planes ixed on t-he said framework one in front of the other and eachl slightly inclined upwardly and forwardly,s'ide sustaining planes fixed on the said framework and extending between the ends bf the said main sustaining planesand in the same plane therewith, andV a basket attached to the said framework and extend- 165 ing with its front and rear ends under the said main sustaining-planes. y y 3. An aeroplane, comprising a framework, main sustaining planes fixed on the said framework one in front ofthe other and 110 each inclined upwardly and forwardly, side sustaining planes V'fixed on the said frames work and extending rearwardly from the front main plane, said side planesbeing arranged in thesame plane with the main 11 planes and having their rear ends terminating at points forwardlyof the rear main plane, and a basket attached to the framework and extending between and beneath i the forward and rear main planes.

i 4. An aeroplane, comprising a framework, a front sustaining plane, a rear sustaining plane spaced from the said front sustaining plane, both planes being fixed to the said framework and slightly inclined upwardly and forwardly, side sustaining planes xed on the framework immediately in the rear of the front sustaining plane and near the outer sides thereof, said side planes extendy ing rearwardly from said front plane and terminating at points intermediate the front and rear main planes, ailerons mounted to swing up and down on the framework in the rear of the said side sustaining planes and the spaces between the same and the rear main plane, and manually-controlled means for moving the said ailerons simultaneously and in opposite directions one relative to the other.

5. An aeroplane, comprising a framework, a front sustaining plane, a rear sustaining plane spaced'from the said front plane, both planes being fixed to the said framework and slightly inclined upwardly and forwardly, side sustaining planes ixed on the framework immediately in the rear of the` front sustaining plane, near the outer sides thereof, and extending rearwardly and terminating at points forwardly of the rear main plane, said side planes being arranged in the same plane with the said main planes, ailerons 'mounted on the framework to swing in the spaces. between the rear'ends of said side planes and the' said rear main plane, and a basket fixed to the framework and extending between ,and beneath the lprovided witha lower fork pivotally mounted in the fram work, connections between one of the said ,udders and an intermediate point on the said steering post, a steering wheel having its shaft extending through and rotatable within thesaid steering post and provided with a lateral extension. at its lower end, the axis of said lateral extension in its normal position being in line with that of the pivot of said steering post, and connections between said lateral extension and the other of said rudders. 1

8. An aeroplane, comprising a framework, sustaining planes -carried by said framework, vertical and horizontal rudders movably1 mounted in said framework, ailerons mounted on opposite sides of the framework and movable in relatively opposite directions, a steering post having a forked lower end pivotallymounted'in the framework, a

connection between one of the rudders and a point intermediate the ends of the steering post, steering wheels having shafts one within the other and bothfexten'ding through said steering post and proyided with lateral extensions at one end projecting in opposite directions and in substantially` the same plane with the axis of the pivotof said steering post, connections between one of said lateral extensionsvand the other ofthe rudders, and connections` between the" other lateral extension and t-he said ailerons.

9. An aeroplane, comprising a framework, sustaining planes carried'by the said framework, transverse shafts journaled at opposite sides of the'framework, ailerons secured upon the outer ends of said shafts, and normally extending in horizontal planes, angular levers rigidly secured to the inner ends of said shafts, a transverse rocking lever intermediately pivoted in the 'framework and with the ends of whichI are pivotally connected the ends of said angular levers, and connections whereby to rock said intermdiately pivoted-lever and swing the ailerons in oppositely relative directions.

In testimony whereof .I have signed my name to this specification in the presence of two subscribing witnesses.

FREDERICK' C. LAMBERT.

Witnesses:

THEO. G. I-Iosfltan, PHILIP D. RoLLHAUs. 

